CN205837175U - A kind of aircraft cockpit steerable system and the physical interface being applied thereon - Google Patents
A kind of aircraft cockpit steerable system and the physical interface being applied thereon Download PDFInfo
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- CN205837175U CN205837175U CN201620466389.3U CN201620466389U CN205837175U CN 205837175 U CN205837175 U CN 205837175U CN 201620466389 U CN201620466389 U CN 201620466389U CN 205837175 U CN205837175 U CN 205837175U
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- displacement sensor
- pedals
- optical displacement
- side lever
- pair
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Abstract
This utility model relates to flight control technique field, a kind of aircraft cockpit steerable system and the integrated physical interface being applied thereon are provided, including side lever, pedals, flap handle, each side lever and 4 double remaining Optical displacement sensors connect, each pair of remaining Optical displacement sensor and 2 ACE connect, and each side lever is connected by 8 optical cables and 4 ACE；Each pedals and 1 double remaining Optical displacement sensor connect, and each pair of remaining Optical displacement sensor and 2 ACE connect, and each pedals are connected by 2 optical cables and 2 ACE；Flap handle and 2 double remaining Optical displacement sensors connect, and each pair of remaining Optical displacement sensor and 2 ACE connect, and flap handle is connected by 4 optical cables and 4 ACE；The beneficial effects of the utility model: system is simple, modularity, be easily integrated；Redundant configurations is reasonable, cable is few；Using Optical displacement sensor, signals collecting real-time is good, strong interference immunity.
Description
Technical field
This utility model relates to aircraft flight and controls technical field, particularly to a kind of aircraft cockpit steerable system and should
For physical interface thereon.
Background technology
The flight control system of aircraft typically by driving cabin steerable system, fly to control electronics and actuator and form, driving cabin is grasped
Vertical system mainly realizes the control command input of driver, flies to control the instruction that mainly realizes according to driver of electronics and realizes control law
Resolving, and export to actuator perform；Actuator system carries out the deflection of aircraft rudder surface according to the instruction flying control electronics, it is achieved
The closed loop control of rudder face.
Traditional driving cabin steerable system is made up of side lever, pedal, flap handle, and driver-operated input is by installing
The RVDT sensor of each operating mechanism realizes, and flying to control electronics provides the resolving of control signal, it is provided that the amount of pilot control input
Change data.
Fig. 1 is traditional driving cabin steerable system structural representation, and the problem that this implementation is brought is the system integration
Complicated: 1, pilot control component sensors is by flying control electronic power, fly to control electronics and reoffer the resolving of signal, system cross-links
By force, coupling is strong, and integrated difficulty is big.2, RVDT sensor complex, each sensor is made up of 5 lines, and in order to ensure
Remaining, each operating mechanism is equipped with multiple RVDT sensor, brings the complexity of realization, and wiring quantity increases, and weight increases
Add.
In prior art with the application closest to technical scheme as follows:
As in figure 2 it is shown, as a example by side lever, single side lever uses 8 single remaining RVDT sensors, and each two RVDT completes to bow
Facing upward and the collection of rolling signal, a corresponding data concentrator or flight control computer or actuator control electronics (ACE), each
RVDT is made up of 5 lines, and totally 40 lines inside side lever, two RVDT are integrated at side lever end, form 4 bursts of totally 20 lines and data
Concentrator cross-links.
Single pedals use 2 single remaining RVDT sensors, the corresponding data concentrator of each sensor, often
Individual RVDT is made up of 5 lines, formed 2 strands totally 10 lines cross-link with data concentrator.
Single flap handle uses 4 single remaining RVDT sensors, the corresponding data concentrator of each sensor or
Flight control computer or actuator control electronics, and each RVDT is made up of 5 lines, formed 4 strands totally 20 lines enter with data concentrator
Row crosslinking.
Prior art has the disadvantages that
1, integration complexity is high；Handle the collection of signal in order to realize driving cabin, need to dispose between each control member
Multiple sensors, the most also need to be simulated signals collecting and resolving flying to control in electronics, and the system degree of cross linking is big, and coupling is strong,
Interface definition is high with the complexity realized, and integrated difficulty is big；
2, number of cables is many, and volume is big with weight；Each operating mechanism, in order to ensure remaining, is equipped with multiple RVDT sensing
Device, each sensor just can be completed function by 5 lines, and the number of cables causing system is many, and volume is big with weight；
3, system restructural degree is low.
Utility model content
The purpose of this utility model overcomes the deficiencies in the prior art exactly, it is provided that a kind of aircraft cockpit steerable system and
The physical interface being applied thereon.
This utility model one aircraft cockpit steerable system, including side lever, pedals, flap handle, throttle
Platform, described side lever, pedals, flap handle be all connected with data concentrator by double remaining Optical displacement sensors, institute
State data concentrator to be connected with flight control computer or actuator control electronics.
Further, this aircraft cockpit steerable system includes 2 side levers, 2 pedals.
Further, the double remaining Optical displacement sensors of each side lever and 4 connect, each pair of remaining Optical displacement sensor with
2 data concentrators connect, and each side lever is connected by 8 optical cables and 4 data concentrators.
Further, each pedals and 1 double remaining Optical displacement sensor connect, and each pair of remaining light displacement passes
Sensor and 2 data concentrators connect, and each pedals are connected by 2 optical cables and 2 data concentrators.
Further, described flap handle and 2 double remaining Optical displacement sensors connect, and each pair of remaining light displacement passes
Sensor and 2 data concentrators connect, and described flap handle is connected by 4 optical cables and 4 data concentrators.
Further, described pair of remaining Optical displacement sensor includes the subassembly set that 2 sets are identical, every subcomponents set
Including optical signal generator, optical signal acquisition device, optical signal modulator, optical fiber cable, photo-detector, every subcomponents set can
The generation of complete independently optical signal, gather, measure, modulate, demodulate, it is achieved changed by the signal of physical quantity to digital quantity.
This utility model additionally provides a kind of integrated physical interface being applied to above-mentioned aircraft cockpit steerable system, described
2 side levers, 2 pedals, the manipulation signal transport vehicle physical integrations of flap handle are integrated, described integrated physics
Interface includes that 8 physical interfaces corresponding to single described side lever, 2 physics corresponding to single described pedals connect
Mouthful, corresponding to 4 physical interfaces of described flap handle；Wherein, each pair of remaining Optical displacement sensor corresponds respectively to 2
Physical interface.
This utility model provides a kind of method handling above-mentioned aircraft cockpit steerable system, including:
Side lever is connected with data concentrator, so that the manipulation signal of each side lever passes through by double remaining Optical displacement sensors
4 double remaining Optical displacement sensors are transferred to the step of 4 data concentrators；
Pedals are connected with data concentrator by double remaining Optical displacement sensors, so that each pedals behaviour
Vertical signal is transferred to the step of 2 data concentrators by 1 double remaining Optical displacement sensor；And
Flap handle is connected with data concentrator by double remaining Optical displacement sensors, so that flap stick control letter
The step of 4 data concentrators number it is transferred to by 2 double remaining Optical displacement sensors.
The beneficial effects of the utility model are:
1, flight control system dispose simple, efficiently, modularity, be easily integrated；
2, rational redundant configurations scheme so that driving cabin operating mechanism i.e. meets the requirement of flight control system entirety remaining,
Realize again the minimizing of the number of cables of system, the reduction of volume, alleviating of weight；
3, using Optical displacement sensor, the collection real-time of signal is higher, and anti-interference is higher.
Accompanying drawing explanation
Fig. 1 show tradition driving cabin steerable system schematic diagram.
Fig. 2 show side lever connection diagram in tradition driving cabin steerable system.
Fig. 3 show this utility model embodiment one driving cabin steerable system schematic diagram.
Fig. 4 show side lever connection diagram in this utility model embodiment.
In figure: bar, 2-right-hand rod, 3-pedals, 4-flap handle on the left of 1-.
Detailed description of the invention
This utility model specific embodiment is described in detail below in conjunction with concrete accompanying drawing.It should be noted that, following enforcement
Technical characteristic described in example or the combination of technical characteristic are not construed as isolating, and they can be mutually combined
Thus reach superior technique effect.In the accompanying drawing of following embodiment, the identical label that each accompanying drawing is occurred represents identical
Feature or parts, can be applicable in different embodiment.
As it is shown on figure 3, this utility model embodiment one aircraft cockpit steerable system, (respectively left including side lever 1,2
Side lever 1, right-hand rod 2, it is possibility to have other side lever arrangement), pedals 3, flap handle 4, throttle platform, described
Side lever 1,2, pedals 3, flap handle 4 be all connected with data concentrator by double remaining Optical displacement sensors, described
Data concentrator controls electronics with flight control computer or actuator and is connected.
Preferably, aircraft cockpit steerable system includes 2 side levers 1,2,2 pedals 3.
Preferably, each side lever (1 or 2) is connected with 4 double remaining Optical displacement sensors, each pair of remaining light displacement sensing
Device and 2 data concentrators connect, and each side lever (1 or 2) is connected by 8 optical cables and 4 data concentrators.Fig. 4 shows
Double remaining Optical displacement sensors of single side lever and the concrete annexation of data concentrator.
Preferably, each pedals 3 are connected with 1 double remaining Optical displacement sensor, and each pair of remaining light displacement passes
Sensor and 2 data concentrators connect, and each pedals 3 are connected by 2 optical cables and 2 data concentrators.
Preferably, described flap handle 4 is connected with 2 double remaining Optical displacement sensors, and each pair of remaining light displacement passes
Sensor and 2 data concentrators connect, and described flap handle 4 is connected by 4 optical cables and 4 data concentrators.
Preferably, described pair of remaining Optical displacement sensor includes the subassembly set that 2 sets are identical, every subcomponents set bag
Including optical signal generator, optical signal acquisition device, optical signal modulator, optical fiber cable, photo-detector, every subcomponents set can be only
Stand the generation of optical signal, gathered, measure, modulate, demodulate, it is achieved changed by the signal of physical quantity to digital quantity.
This utility model embodiment is for the integrated physical interface of above-mentioned aircraft cockpit steerable system, described 2 side levers
(1,2), 2 pedals 3, the manipulation signal transport vehicle physical integrations of flap handle 4 are integrated, described integrated physics
Interface includes 8 physical interfaces corresponding to single described side lever (1 or 2), corresponding to single described pedals 32
Physical interface, 4 physical interfaces corresponding to described flap handle 4；Wherein, each pair of remaining Optical displacement sensor is the most right
Should be in 2 physical interfaces.
A kind of method handling above-mentioned aircraft cockpit steerable system, including:
Side lever (1 or 2) is connected with data concentrator by double remaining Optical displacement sensors, so that each side lever (1 or 2)
Handle signal and be transferred to the step of 4 data concentrators by 4 double remaining Optical displacement sensors；
Pedals 3 are connected with data concentrator by double remaining Optical displacement sensors, so that each pedals 3
Handle signal and be transferred to the step of 2 data concentrators by 1 double remaining Optical displacement sensor；And
Flap handle 4 is connected with data concentrator, so that flap handle 4 is handled by double remaining Optical displacement sensors
Signal is transferred to the step of 4 data concentrators by 2 double remaining Optical displacement sensors.
In this utility model embodiment, side lever 1,2 mainly realizes the manipulation input of pilot, including fore-and-aft control, horizontal stroke
To handling and Autopilot Disengage Switch, the manipulation of pilot is inputted to gather and uses double remaining light displacement sensing by this utility model
Device, is sent to data concentrator after signal condition, it is achieved the vertical and horizontal operating function of pilot.
Pedals 3 mainly provide the manipulation on pilot course to input, it is achieved the input to rudder control, and then
Realizing Heading control, the manipulation of pilot is inputted to gather and uses double remaining Optical displacement sensor, signal condition by this utility model
It is sent to data concentrator afterwards, it is achieved the operating function in pilot course.
Flap handle 4 mainly provides the manipulation of pilot's Air slowdown to input, this utility model manipulation to pilot
Input gathers the mode using double remaining Optical displacement sensors, is sent to data concentrator, it is achieved pilot after signal condition
The operating function of Air slowdown.
Optical displacement sensor uses double redundancy design, and each pair of remaining Optical displacement sensor has the optical signal that two sets are identical
Generator, optical signal acquisition device, optical signal modulator, optical fiber cable and photo-detector, it is achieved the backup functionality of sensor.
The beneficial effects of the utility model are:
1, flight control system dispose simple, efficiently, modularity, be easily integrated；
2, rational redundant configurations scheme so that driving cabin operating mechanism i.e. meets the requirement of flight control system entirety remaining,
Realize again the minimizing of the number of cables of system, the reduction of volume, alleviating of weight；
3, using Optical displacement sensor, the collection real-time of signal is higher, and anti-interference is higher.
Although having been presented for several embodiment of the present utility model herein, but those skilled in the art should managing
Solve, in the case of without departing from this utility model spirit, the embodiments herein can be changed.Above-described embodiment simply shows
Example, should be using the embodiments herein as the restriction of this utility model interest field.
Claims (7)
1. an aircraft cockpit steerable system, including side lever, pedals, flap handle, throttle platform, its feature exists
In, described side lever, pedals, flap handle are all connected with data concentrator by double remaining Optical displacement sensors, institute
State data concentrator to be connected with flight control computer or actuator control electronics.
2. aircraft cockpit steerable system as claimed in claim 1, it is characterised in that include 2 side levers, 2 rudder feet
Pedal.
3. aircraft cockpit steerable system as claimed in claim 2, it is characterised in that each side lever and 4 double remaining light positions
Displacement sensor connects, and each pair of remaining Optical displacement sensor and 2 data concentrators connect, and each side lever passes through 8 optical cables and 4
Individual data concentrator connects.
4. aircraft cockpit steerable system as claimed in claim 2, it is characterised in that each pedals and more than 1 pair
Degree Optical displacement sensor connects, and each pair of remaining Optical displacement sensor and 2 data concentrators connect, and each pedals lead to
Cross 2 optical cables and 2 data concentrators connect.
5. aircraft cockpit steerable system as claimed in claim 2, it is characterised in that described flap handle and more than 2 pairs
Degree Optical displacement sensor connects, and each pair of remaining Optical displacement sensor and 2 data concentrators connect, and described flap handle leads to
Cross 4 optical cables and 4 data concentrators connect.
6. the aircraft cockpit steerable system as described in any one of claim 1-5, it is characterised in that described pair of remaining light displacement
Sensor includes that the subassembly set that 2 sets are identical, every subcomponents set include optical signal generator, optical signal acquisition device, light
Signal modulator, optical fiber cable, photo-detector, every subcomponents set can complete independently optical signal generation, gather, measure,
Modulation, demodulation, it is achieved changed by the signal of physical quantity to digital quantity.
7. the integrated physical interface being applied to aircraft cockpit steerable system as claimed in claim 2, it is characterised in that
Described 2 side levers, 2 pedals, the manipulation signal transport vehicle physical integrations of flap handle are integrated, described integrated
Physical interface includes 8 physical interfaces corresponding to single described side lever, 2 physics corresponding to single described pedals
Interface, 4 physical interfaces corresponding to described flap handle；Wherein, each pair of remaining Optical displacement sensor corresponds respectively to 2
Individual physical interface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620466389.3U CN205837175U (en) | 2016-05-19 | 2016-05-19 | A kind of aircraft cockpit steerable system and the physical interface being applied thereon |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620466389.3U CN205837175U (en) | 2016-05-19 | 2016-05-19 | A kind of aircraft cockpit steerable system and the physical interface being applied thereon |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205837175U true CN205837175U (en) | 2016-12-28 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620466389.3U Withdrawn - After Issue CN205837175U (en) | 2016-05-19 | 2016-05-19 | A kind of aircraft cockpit steerable system and the physical interface being applied thereon |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205837175U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105857581A (en) * | 2016-05-19 | 2016-08-17 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Airplane cockpit control system and method |
-
2016
- 2016-05-19 CN CN201620466389.3U patent/CN205837175U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105857581A (en) * | 2016-05-19 | 2016-08-17 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Airplane cockpit control system and method |
| CN105857581B (en) * | 2016-05-19 | 2018-10-02 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of aircraft cockpit steerable system and method for operating |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20161228 Effective date of abandoning: 20181002 |
|
| AV01 | Patent right actively abandoned |